EP1797319B1 - Moteur de poussee a particules chargees - Google Patents

Moteur de poussee a particules chargees Download PDF

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Publication number
EP1797319B1
EP1797319B1 EP05858401.2A EP05858401A EP1797319B1 EP 1797319 B1 EP1797319 B1 EP 1797319B1 EP 05858401 A EP05858401 A EP 05858401A EP 1797319 B1 EP1797319 B1 EP 1797319B1
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Prior art keywords
electrodes
charged particles
charged particle
thrust
electric field
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EP1797319A2 (fr
EP1797319A4 (fr
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Tristram Walker Metcalfe, Iii
Walter Timmons Cardwell, Jr.
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00—Using plasma to produce a reactive propulsive thrust
    • F03H1/0037—Electrostatic ion thrusters

Definitions

  • thrust is produced by ionizing neutral atoms or molecules and accelerating these ions, the reaction mass, by an electric field.
  • the amount of thrust is equal to the reaction mass times the acceleration of that mass or the reaction mass times the change in velocity of the mass.
  • energy must be supplied to that mass.
  • the energy that must be supplied is equal to one half the mass times the change in velocity of the mass squared.
  • Maximum energy efficiency is obtained by creating the greatest thrust for the least amount of supplied energy. Energy efficiency can be maximized by accelerating the largest reaction mass possible to the minimum velocity necessary to achieve the desired thrust.
  • reaction mass In space applications, especially where energy can be obtained from solar energy or nuclear sources, the reaction mass must be minimized since it must be carried by the spacecraft itself. In this situation you want to accelerate the smallest mass to the highest velocity possible. You are minimizing the expenditure of mass by using relatively large amounts of energy.
  • the overall energy efficiency of ion engines is very low when mass is being minimized but the thrust per unit mass is very high. Because the amount being accelerated is so small, most ion engines are only able to generate a few ounces of thrust at most. Still, in space applications where reaction mass is limited, they can be far more efficient than conventional rockets.
  • these attempts consisted of two electrodes, the first either a thin wire supported over the second electrode that is either a flat plate aligned with the wire so that the thin edge of the plate is pointed toward the wire as in FIG. 1A or as a grid as shown in FIG. 1B , or the first electrode is a sharp point coaxial to a second ring electrode spaced at some distance from the first electrode as shown in FIG. 1C .
  • a high voltage is then applied between the two electrodes and if the device is light enough and the voltage is sufficient, it will rise off the ground.
  • Robert S. Fritzius combined two pairs of electrodes of opposite polarity so that once the ions were accelerated, they would neutralize each other.
  • Kenneth E. Burton took the basic Coleman device and reversed the polarity of the electrodes so that negative ions were created instead of positive ions.
  • French patent application published with No. FR 2717865A discloses a propulsion system for the space vehicle in low earth orbit, defined as having an altitude between 160 and 1000 Km.
  • the space vehicle has a leading electrode (Eav) and a rear conducting grid (gar) attached to its chassis.
  • the leading electrode may be either a conducting plate or a grid and the rear grid comprises heated points suitable to discharge electrons.
  • the leading and rear electrodes are maintained at a potential difference by a battery such that an electric field (E) is produced. This field propels ions and electrons in opposite directions.
  • the momentum of the ions is much greater than that of the electrons and the net momentum propels the vehicle by reaction.
  • US 6 145 298 A discloses a method for generating thrust in a charged particle jet engine operating in a gaseous medium according to the preamble of claim 14.
  • ion thrusters In all known applications of ion thrusters in the atmosphere, they are all based on an ionizing electrode (5) in all drawings, either a sharp point FIG. 1C (5) or a thin wire FIG. 1A (5) and FIG 1B (5), separated from an accelerating electrode (4) of either a plate, grid, or ring.
  • the high voltage (8) applied between the two electrodes (3,4) both ionizes and accelerates the ions. While these devices will lift an ounce or two in air, attempts to increase the thrust to useable amounts have so far failed due to the lack of understanding of how to maximize the thrust while minimizing the energy required to generate that thrust.
  • the energy of an object is one half its mass times its velocity squared.
  • the power we must supply is the energy per unit time and is equal to one half the reaction mass flow rate times its velocity squared.
  • the thrust efficiency is equal to two divided by the change in velocity of the reaction mass.
  • the thrust of a charged particle engine is equal to the force on each charged particle, which is equal to the charge on that particle times the instantaneous electric field at each point.
  • the change in momentum of the charged particle is equal to that force times the time the force is applied to the particle.
  • the equal and opposite force on the electrodes is the reaction motor thrust.
  • the thrust efficiency of a charged particle engine is two divided by the final velocity of the charged particles when it leaves the electric field.
  • the critical insight leading to the key features of this invention and what distinguishes it from the prior art is the recognition that, when operating in a medium, the efficiency of the charged particle engine is determined by the velocity of the charged particles at the time of their collision with the neutral molecules of the medium.
  • Ion rockets in space operating in a vacuum, accelerate the ions to a very high velocity which results in more thrust for a given reaction mass but with extremely low thrust efficiency.
  • the charged particles obtain much lower velocities because they are constantly being slowed by collisions with the medium.
  • the key to thrust efficiency in a medium is finding ways to slow the velocity of the charged particles at the time of each collision.
  • the mean free path In any gas, liquid, or solid, there is space between the atoms and molecules. This space is called the mean free path and is a function of the temperature and pressure of the material. It is the distance a particle will travel before colliding with another particle of the medium. In our case, when a charged particle is being accelerated by the electric field, the mean free path determines how far a charged particle will travel before colliding with another particle. If the mean free path is short, the charged particle will not acquire very much energy before colliding with the neutral molecule of the medium. The greater the mean free path, the higher will be the charged particle's velocity and thus the lower its efficiency when it collides with the molecules of the medium.
  • Our invention as claimed in claims 1 and 14 deals with the many steps that can be taken to increase both thrust and thrust efficiency of charged particle engines operating and a medium.
  • the change in momentum is mdv.
  • the critical insight leading to the key features of this invention and what distinguishes it from the prior art is the recognition that electrostatic thrust is totally determined by the charged particles while they are in the electric field and that the thrust efficiency is totally determined by their velocity at the time of their collision with the neutral reaction mass.
  • the force on each charged particle is equal to the charge times the instantaneous electric field at each point.
  • the change in momentum of the charged particle is still equal to the force times the time the force is applied to the particle, equation (1c).
  • the thrust produces a change in momentum of the engine equal to but opposite in direction to the momentum of the charged particles.
  • the velocity of the charged particle at the time of the collision with the neutral reaction mass is still the energy of the charged particle given by equation (1d).
  • the energy given to a particle between collisions is equal to the charge times the electrical potential of the particle just after the previous collision and the electrical potential just at the point of the next collision.
  • the mean free path In any gas, liquid, or solid, there is space between the atoms and molecules. This space is called the mean free path and is a function of the temperature and pressure of the material. It is the distance a particle will travel before colliding with another particle of the medium. In our case, when a charged particle is being accelerated by the electric field, the mean free path determines how far a charged particle will travel before colliding with another particle. If the mean free path is short, the charged particle will not acquire very much energy before colliding with the neutral reaction mass molecule. The greater the mean free path, the higher will be the charged particle's velocity and thus the lower its efficiency when it collides with the neutral reaction mass molecule.
  • the problem is the reverse electric field generated by the charged particles traveling between the electrodes. When the number of charges is great enough, this reverse electric field can completely cancel the applied electric field at the inlet electrode. To compensate for this low electric field, the applied voltage must be increased to the point that by the time you are able to get enough thrust the ion velocity has become so great at the exit electrode due to the relatively large mean free path, that the overall transfer efficiency is only a fraction of a percent.
  • the electrostatic thrust and efficiency is determined by the mean free path.
  • the mean free path is the same in all directions.
  • the mean free path in the direction of the particle acceleration increases.
  • the component of thrust due to the equal mean free path we call the mobility thrust as the thrust is determined by the mobility of the charged particles in the reaction thrust medium.
  • the component of thrust due to the increase in the mean free path as the reaction mass is accelerated we call the effective mass thrust.
  • the effective mass energy transfer efficiency can approach 100% even with the space charge induced reverse electric field.
  • the mobility thrust efficiency when the reverse electric field is included is usually less that 1%. It is the mobility thrust component that is most severely affected by the reverse electric field because the rather large mean free path allows the charged particles to attain high velocities when the applied acceleration voltage is increased to compensate for the reverse electric field.
  • thermodynamic energy can be partially recovered or partially turned into thermodynamic thrust or both.
  • the first step in generating efficient electrostatic thrust is to decouple ion generation from ion acceleration. This allows us to control the accelerating voltage and thus the efficiency independently of the voltage needed for ion generation.
  • the quantity V/L is the applied electric field strength and from equation (2b), reducing this term linearly increases efficiency but reduces thrust as the square of the electric field reduction. But we can increase efficiency by decreasing the mobility.
  • the mobility is inversely proportional to the pressure of the medium so we can increase efficiency by converting the acquired velocity of the reaction mass as it passes through the engine to a pressure increase by enclosing the electrodes in a non conducting tube and slowly decrease the cross sectional area of the tube from inlet to exhaust to increase the pressure accordingly.
  • the first method used to alter the radial and/or angular electric field strengths is to change the shape of the electrodes to create complex three dimensional electric fields were the radial and angular changes in the electric field are enhanced at the expense of the axial electric field.
  • the second method is to use a non-uniform radial and/or angular charged particle density so that the self-induced radial and/or angular change in the electric field reduces the change in the axial electric field strength.
  • a third method is to use additional electrodes between the accelerating electrodes to create a radial and/or angular component of the electric field. These electrodes can be insulated if necessary to prevent neutralization of the charged particles.
  • a fourth method is to employ current carrying insulated regions imbedded in the region between the accelerating electrodes carrying oppositely charged particles whose space charge generated electric field completely or partially cancels the reverse electric field of the thrust producing charged particles. These oppositely charged regions could be charged particles producing thrust just of opposite sign or they could be non thrust producing charged particles such as electrons the eventually neutralize the thrust producing charged particles.
  • a fourth method is to make these oppositely charged regions coaxial.
  • Another method to increase thrust and/or efficiency is to segment the engine.
  • multiple electrodes are used to create the equivalent of several engines in tandem with charged particles fed mainly to the first electrode and where the potential of each succeeding electrode increases so that the charged particles are moved through all the stages.
  • These intermediate electrodes could either be insulated or additional charged particles could be injected to replace those particles neutralized passing through the intermediate electrodes.
  • the intermediate electrode could also be looked at as fixed potential surfaces that counteract the reverse electric field generated by the space charge.
  • the thrust is increased by the number of stages used, while the efficiency can be increased by reducing the applied voltage between each segment.
  • Another method to increase thrust and efficiency is to increase the charged particle current while reducing the applied voltage.
  • the only way to do this without changing the mobility or density of the medium is to increase the number of charged particles that make up the charged particle current.
  • increasing the number of charges between the accelerating electrodes increases the reverse space charge until the point where they prevent any additional charged particles from entering the inlet region. If any additional charged particles enter the region, the reverse electric field becomes greater than the applied electric field and the charged particles are forced away from the inlet.
  • the current that flows due to an electric field is called the drift current.
  • a diffusion current is caused by any concentration gradient.
  • the diffusion current is independent of the drift current and can actually flow in the opposite direction from the drift current. If we increase the charged particle concentration gradient at the inlet electrode, we can create a diffusion current that will flow against the space charge generated reverse electric field.
  • the diffusion current is equal to a diffusion coefficient times the concentration gradient.
  • the charged particles in this high concentration gradient region also generate an electric field and the magnitude of this electric field must be kept below the breakdown electric field of the medium. Even though the diffusion coefficient is usually and order of magnitude less than the mobility to which it is related, the concentration gradient can be quite high so that the diffusion current can actually be more than an order of magnitude greater than the space charge limited drift current.
  • this concentration gradient is also possible to use with the segmented engine and where the high concentration gradient is propagated between the stages.
  • the diffusion current will oppose the reverse drift current and eventually the diffusion current will reach a positive net acceleration voltage between the electrodes. At this point, the drift and diffusion currents will be in the same direction.
  • the end of a segment is reached, there will again be a net electric field opposing the charged particle current flow.
  • the charged particles from the first stage will concentrate at the inlet of the second stage until the diffusion current associated with this concentration gradient counteracts the reverse drift current of this next stage. The result of this is the propagation of the concentration gradient through the stages of the engine.
  • either a physical barrier or an electrical one can be used to create the charged particle concentration gradient. If we pump charged particles into the inlet region and if we prevent them from escaping out the front of the engine, they will build up in concentration until they do flow into the engine.
  • An insulated physical barrier can be used or a cap electrode can be used that creates an electric field that prevents the charged particles from escaping.
  • the increase in temperature as the reaction mass is being accelerated through the engine results in the thermal motion of the neutral mass being greater at the exhaust than the intake. Because the thermal velocity is in all directions, half the neutral molecules will have a component of this thermal velocity going from back to front. Because the thermal velocity at the exit electrode is greater than the thermal velocity at the inlet, there will be a net flow of charged particles due to the different thermal velocities from exit to inlet. When these neutral molecules collide with a charged particle, the momentum associated with this velocity component is transferred back to the charged particle causing the charged particle to either not draw as much energy from the electric field or to return energy to the field.
  • thermodynamic energy can be converted into thrust exactly in the same way as it is converted in a conventional chemical jet engine. If the reaction mass can only leave through the exhaust, the pressure difference between the front of the engine and the rear of the engine will produce thrust. To convert this thermodynamic pressure into thrust, the engine must be enclosed whereby the neutral air mass is prevented from escaping except through the exhaust opening.
  • the basic structure of our charged particle jet engine device uses a plurality of electrodes connected to an electrical power source, at least one of said electrodes when immersed in a gaseous particle medium allows the medium to pass through or around it.
  • the size, shape, and position of the electrodes and other structures in the medium create different regions of the medium used by the device.
  • the introduction of low energy charged particles at any point in said medium or the separation of charged particles that are already in the medium assure that the majority of charged particles if any in a region are of one polarity. These charged particles are accelerated by one or more electric fields produced by potential differences between electrodes.
  • the accelerated charged particles travel a sufficient distance in the medium so that the number of collisions of said accelerated charged particles with atoms and/or molecules of the medium result in the transfer of energy and momentum from the charged particles to the neutral atoms or molecules.
  • the total mass of the neutral atoms and/or molecules that collide with the charged particles exceeds the total mass of the charged particles so that the energy and momentum of the neutral atoms and/or molecules that have collided with the accelerated charged particles exceeds the mass, energy and momentum of the accelerated charged particles after leaving the region of the device where the charged particles were accelerated and where the charged particles that are used to transfer energy and momentum to the neutral atoms and/or molecules to produce thrust are not created by high voltage ionization due to the electric fields of any of the accelerating electrodes.
  • One or more of the electrodes surrounds a given region in the medium and is of any size and shape and is immersed either partially or completely in the medium.
  • One or more of the electrodes is made of a non insulating material or is covered totally or partially by an insulating material which allows the medium and any charged particles in the medium to pass through or around it. When one or more of the electrodes allows the charged particles to pass through or around the electrode some or all of the charged particles remain charged.
  • the area enclosed by one or more electrodes can be fixed or variable.
  • One or more of the electrodes neutralizes some or all of the charged particles passing through or around the electrode.
  • the electrodes can be held together and supported by a series of structures insulated from at least one electrode wherein such structure is of sufficient strength to withstand the mechanical and electrostatic forces placed on it and on any material or structure attached to it.
  • the structures can be rigid and/or adjustable such that both the spacing and orientation of the electrodes with respect to each other can be adjusted.
  • the method used to adjust the structures can be mechanical, electrical or hydraulic. It is possible with the invention to transfer the thrust, momentum, energy, and motion of the structure to another structure of sufficient strength to withstand the mechanical and electrostatic forces placed on it and on any material or structure attached to it or to incorporate or merge the charged particle jet engine structures into another structure of sufficient strength.
  • the invention can be constructed so that one or more structures through which the medium cannot flow are used to control and direct the medium flow.
  • the structures can partially enclose one or more regions of the medium forcing the medium to flow into and out of these regions through openings in the structure.
  • the axial space charge generated electric field can be reduced using a nonuniform electric field perpendicular to the axial space charge generated electric field which can be a radial electric field, an angular space charge generated electric field or a nonuniform charge density.
  • One method used to reduce the axial space charge generated electric field can consist of one or more additional electrodes, conductors, and channels any of which can be insulated or not and which can be axial, radial, and/or angular electrodes, conductors, and/or channels.
  • a second method used to reduce the axial space charge generated electric field consists of one or more adjacent or coaxial axial thrust producing regions wherein the charged particles are of a polarity where the space charge generated electric fields of all of the regions can be made to partially or completely cancel the space charge generated electric fields of each of the regions.
  • the space charge limited current flow can be increased through the use of a diffusion current wherein the greater the concentration gradient of the charged particles, the greater will be the diffusion current and therefore the space charged limited current.
  • Two methods of increasing the concentration gradient of the charged particles are through the use of one or more additional closely spaced electrodes that create an electric field that concentrates the charged particles at the desired location and/or through the use of one or more insulated structures that form a physical barrier preventing the charged particles from leaving in all but the desired direction.
  • thermodynamic energy of the reaction mass through the interaction of high energy neutral atoms and/or molecules with charged particles in some region of the engine and we can maximize the energy recovery by concentrating charged particles in a region of interaction of the neutral atoms and/or molecules and the charged particles through the use of one or more additional electrodes and/or through the use of one or more structures that form a physical barrier preventing the charged particles from leaving in all but the desired direction.
  • thermodynamic energy can also convert some of the thermodynamic energy to thrust by preventing the neutral reaction mass from flowing out the inlet of one or more of the thrust producing regions as thermodynamic energy is added to the reaction mass by changing the direction and/or velocity of the neutral atoms and/or molecules whereby the change in momentum of the neutral atoms and/or molecules must be matched by an equal but opposite change in momentum of the charged particle jet engine resulting in increasing the thrust of the engine.
  • Charged particle jet engines can be combined in three ways to increase either thrust, efficiency, or both. Simply using multiple independent charged particle engines is one way but the input area, energy use, and weight increase linearly with the number of charged particle engines used. Placing two or more independent charged particle jet engines in tandem where the neutral reaction mass output of one charged particle jet engine is fed into the input of another charged particle jet engine will increase thrust, energy use, and weight linearly with the number of stages while the input area will remain constant. Placing two or more merged charged particle jet engines where the output electrode of one engine is the input electrode of the next charged particle jet engine produces a segmented charged particle jet engine where the thrust, energy, and weight increase linearly with the number of stages while the input area and the ion generation energy will remain constant. For the segmented configuration, each electrode in sequence must be at a higher electrical potential that the preceding electrode. For the tandem configuration, the electrode potentials can be independent of each other because no charged particles are transferred between charged particle jet engines.
  • the charged particles must either be removed from the reaction mass or neutralized when they are no longer needed.
  • Charged particles can be separated from the reaction mass by electromagnetic fields and once separated can be either stored, neutralized or recirculated. At the same time the particles are separated, they can be sorted by mass so that whether a charged particle is neutralized, stored, or recirculated can be based on the mass of the charged particle.
  • the accelerating electrostatic field will cause the charged particles to be attracted to the exit electrode. If this electrode is made conductive, it will neutralize the charged particles.
  • the charged particles can also be neutralized by injecting the opposite polarity charges from the ion generator into the region where the charged particles are to be neutralized or by letting the charged particles form opposite polarity thrust producing regions neutralize each other. If the charged particles are to be recirculated, electromagnetic forces can be used to direct and accelerate the recirculating charges. It is also possible to use a mechanical transport means such as a mechanical pump to recirculate the charged particles. If the charged particles are not created from the medium, it may be advantageous to first neutralize the charged particles and transport them to the input of a charged particle generator.
  • a collecting scoop can be inserted into the medium to increase the amount of the medium that enters a region.
  • the use of alternate electrodes can be used to select which region the neutral medium enters.
  • the electrical methods have the advantage of direct electrical control of the thrust trajectory and no moving parts.
  • the charged particles can be either created directly in the appropriate region through photon ionization and/or through electron or other particle collisions of sufficient energy.
  • Corona discharge is a special case of particle collisions that uses a high electric field to produce a cascade of charged particles.
  • the traditional use of corona discharge produced by a high electric field between the inlet and output accelerating electrodes guarantees the lowest efficiency possible as the charged particles, once they are created, are accelerated through the maximum potential possible for a given electrode spacing.
  • Corona discharge can be used to create ions directly in a region at high efficiency if both of the electrodes producing the high electric field are not the same as both the inlet and output accelerating electrodes.
  • the source of these charged particles can be stored charged particles either created from some medium or particles that have a permanent static charge, charged particles created from a medium other than the medium accelerated by the charged particles, and/or from the same medium that the charged particles accelerate and form the neutral reaction mass.
  • the charged particle generator can be an ion generator that uses a high electric field, electromagnetic radiation and/or particle collisions including corona discharge to generate ions using the minimum energy possible to create the ions. If excess energy is used in creating the charged particles, it can be recovered through the interaction of the charged particle and an electric field.
  • the medium itself can contain sufficient charged particles to produce the required thrust and by ensuring that in any region of the charged particle engine where the charged particles are used to supply energy to the neutral medium that the majority of the charged particles in the region have the same polarity either through separation or through selective neutralization.
  • Thrust can be varied by varying the potentials applied to the accelerating electrodes, varying the quantity and/or distribution of the charged particles in a thrust producing region of the charged particle jet engine, varying the space charge generated reverse electric field by varying the potentials and/or currents of any space charge generated reverse electric field minimizing electrodes or conductors and/or by controlling the amount of neutral reaction mass that is available in a thrust producing region.
  • the amount of neutral reaction mass available and/or the number of charged particles available in a region can be controlled by a mechanical throttle and/or by electrodes that direct some or all of the charged particles to a non thrust producing region of the charged particle ion engine and direct the neutral reaction mass particles to a non thrust producing region by collisions with charged particles.
  • a charged particle jet engine of any size packaged as self contained unit containing one or more ion generators, one or more ion acceleration regions, a power source, a power supply, fuel, and control electronics will create a stand alone self contained source of a force that can be applied to any object where the application of such a force has meaning.
  • the charged particle jet engine can also be integrated into the structures such as, but not limited to, vehicles and self contained unit above. Integrating the charged particle jet engine into some other structure can result is tremendous savings in materials, cost, and/or weight.
  • an enclosed charged particle jet engine could be integrated into the airframe of a jet aircraft where a single structural tube would provide the support for embedded accelerating electrodes, would at the same time provide a large area structural support for a fuel cell and/or a solar cell greatly reducing weight.
  • the choice of fuel and power source would depend on the application but could be one or a combination of a battery, a solar cell, a fuel cell, and/or some form of a nuclear reactor.
  • the charged particle jet engine can be used as a means to move the medium in which it is embedded instead of moving itself. It can be used as a fan and/or pump that move a potentially unlimited volume of a gaseous medium such as air or other gas.
  • a charged particle jet engine to move a gaseous medium
  • the one or more charged particle jet engines can be temporarily or permanently attached to the object and if permanently attached can be integrated into the objects structure.
  • the objects to which the one or more charged particle jet engines apply their force to will be partially or completely immersed in the reaction mass medium.
  • the other two orthogonal axis are at right angles to the vertical axis. If there is no detectable gravitational force, the orientations of the axis are arbitrary. These axis can be used to define the position, orientation, distance, and velocity of the object and the direction of the forces that are applied to the object.
  • the charged particle jet engines can be aligned with the axis or not depending on the application.
  • the forces on the objects are not limited to forces produced by the charged particle jet engines but may also include the gravitational force, static forces such as those produced by wheels or static structures, fluid dynamic forces, buoyant forces, and forces due to inertia.
  • the buoyant and fluid dynamic forces can be those produced by one or more gases and/or one or more liquids.
  • the fluid dynamic forces can be produced or modified by one or more airfoils, one or more hydrofoils, and/or one or more control surfaces on the object where the control surfaces can be either fixed or moveable about any arbitrary axis not necessarily aligned with the global axis mentioned above.
  • Additional fluid dynamic forces can occur at the interface between two different media such as planing on the surface of the medium by such objects as boats and skis, surface tension of the medium, and so the called "ground effect" forces.
  • the total net force on the object can be modified in both magnitude and/or direction by modifying the magnitude and/or direction of any of the individual forces on the object.
  • the magnitude and direction of the forces on the object produced by the one or more charged particle jet engines can be modified by any of the methods given above.
  • the fluid dynamic forces can be modified by varying the velocity, shape, and/or orientation of the object in the medium or through one or more of the control surfaces.
  • the surface forces can be modified by the object's velocity, shape, orientation with respect to the surface and distance from the surface. Buoyant forces can be modified by varying the size shape or weight of the object.
  • the position, orientation, acceleration, size, shape, and/or velocity of the object can be modified.
  • These parameters can be directly modified by a computer through direct electrical control of the forces on the object.
  • the spacing and relative velocity of the object in relation to any known physical object, not just other charged particle jet engine controlled objects, can be modified and/or maintained by this computer control through sensors on the object or by some traffic control system that is in communication with the object.
  • the fact that the object is under computer control does not prevent manual control from being exercised over the object, "fly by wire".
  • the desired values of any of the parameters controlled by the computer can be entered into the computer and where the computer is connected to a sensor that determines the current value for the parameter, the computer can modify the actual parameter to match the desired value. This allows the parameters to be stabilized under varying conditions such as load, currents and eddies in the medium, and/or varying surface conditions.
  • One of the objects to which one or more charged particle jet engines can be attached is a person.
  • Small engines can be attached to boots worn by the person where the thrust can appear as the same force one would experience standing on a solid surface.
  • a harness can be used to attach one or more the charged particle jet engines to the persons back or the engines can be attached to a flight suit where the force is applied to the body over a wide area.
  • the charged particle jet engine can function as a parachute.
  • additional small control charged particle jets can be attached to gloves so that a force can be exerted on the hands to maintain balance.
  • the amount of force generated by the charged particle jet engines attached to the boots could be regulated by the angle of the ankle so that standing on your toes would increase thrust while standing on you heels would reduce thrust to zero.
  • the same mechanism could be applied to the charged particle jet engines attached to the hands where the angle of the wrist controls the magnitude of the thrust.
  • this guide structure can be in the form of a track that is partially surrounded by part of the object, a track structure that partially surrounds the object, a track structure that completely surrounds the object, a tube structure that partially surrounds the object, a tube structure that completely surrounds the object, a virtual path stored in a computer that uses onboard GPS information and/or an inertial guidance system to match the stored position and velocity with the actual position and velocity as determined by the inertial guidance system and/or the GPS signals, some structure that can be sensed by sensors on the object wherein the structure is either fixed or variable in time and/or space, or where the path consists of one or more electromagnetic signals such as focused light beams that can be sensed by the object's sensors.
  • the constrained path can be defined by a trajectory between the current position of the object and a point in space fixed or variable with respect to time and position.
  • This point is space can be a waypoint, a final or destination point, an other object in space where the object is either moving or stationary.
  • a destination point is a final point where the object can remain without the expenditure of energy.
  • the final point can be a target point where the constrained object can affect some other object at that point, the target object, by destroying it using the kinetic energy of the constrained object, by an explosive chemical or nuclear warhead detonated at or near the target point with the warhead having sufficient energy to destroy the target object.
  • the target point can be the position of an object whose initial position at the target point can be altered by the constrained object attaching to the target object by magnetic, mechanical, or adhesive means and then using the forces applied to the constrained object to move both objects.
  • the target object is a charged particle jet engine controlled object by communication between the constrained object and the target object can be used to force the target object into a path that follows the constrained object.
  • Multiple charged particle jet engine controlled objects can be constrained to follow the same path with a set separation maintained by a mechanical spacer or a sensor that senses the spacing between the objects and where the control mechanism uses the sensors to modify the actual spacing so that it equals the desired spacing thus forming a virtual train.
  • FIG. 2A shows a schematic side view of the various components of this invention.
  • (1) is an arrow indicating the entry point of the gaseous or liquid medium.
  • the arrow labeled (2) points to the exit point of the medium.
  • the rings, (3) and (4) are the electrodes used to create the electrostatic field that accelerates the charged particles in a direction from (3) to (4).
  • the charged particle generator (5) is independent of the electrostatic force acceleration field between the two electrodes (3) and (4).
  • the path (6) is used to introduce the charged particles uniformly into the field between the two accelerating electrodes and while this is shown schematically as a separate tube, this is not meant to rule out charge generation methods that are contained within one or more of the electrodes.
  • the charged particles When the charged particles have reached the exit electrode, they no longer contribute to the thrust of the engine and must be neutralized unless they are to be recirculated or used in stages that follow as discussed later in this document. Because all the charged particles are attracted to the exit electrode, they can be neutralized simply by making the electrode conductive on its surface where the charged particles can either pickup or lose their charge. Because the velocity of charged particles in a medium have been slowed by collisions with the medium, erosion of the electrodes should not be a significant problem.
  • Figures 3 through 21 show various configurations of the invention that are presented to enhance understanding of the principles and flexibility of the invention and are not intended to limit in any way the scope of the invention.
  • Figure 3 illustrates various charged particle jet configurations that may offer certain advantages depending on the application. In these drawings, charged particle generation is omitted for clarity.
  • Figure 3A the basic open frame structure is shown. Here, the two electrodes (3) and (4) are separated by an insulator (7) and provide a medium input (1) and exhaust output (2). This configuration works due to the fact that the force is between the charged particles and the electrodes.
  • Figure 3B encloses the electrodes in an insulating housing (7).
  • Figure 3C shows the addition of a medium scoop or funnel (9) used to increase the number of neutral atoms and molecules entering the engine. The more mass that is moved, the less energy is needed for a given thrust.
  • Figure 3D shows a converging nozzle (10) that can be used to recover part of the energy of the neutral atoms and molecules.
  • Figure 3E shows a diverging nozzle (10) that can also be used to recover this energy.
  • Figure 3F shows a tapered configuration where the cross sectional area decreases going from the entry electrode to the exit electrode that results in an increase in pressure of the neutral atoms and molecules as they travel between the electrodes.
  • Figure 3G show a reverse taper where the pressure decreases from front to back over what it would be if the cross section were not tapered.
  • the tapered walls also convert the perpendicular energy flow of the neutral atoms and molecules into axial thrust through collisions with the housing (7).
  • Figure 3H shows the use of medium inlets (11) around the circumference of the housing used to bring more of the medium into the region between the electrodes. This is especially useful in applications where the electrodes are stationary with respect to the medium and where the purpose of the charged particle jet is to provide static thrust with no relative motion with respect to the medium.
  • Figure 3I shows an additional scoop or funnel (9a) designed to pressurize the air entering the peripheral air inlets. Flapper doors over the inlets can be made to close when the pressure inside the jet is greater than the pressure outside.
  • Figure 3J shows an open frame configuration of the charged particle engine where the electrodes are not circular rings.
  • the electrodes can be of any shape depending on the desired electric field distribution and the space constraints of the design. It should also be quite obvious that the modifications to the open frame structure of Figure 3A shown in Figures 3B through Figure 3I can also be applied to the open frame structure shown in Figure 3J and other arbitrary electrode shapes.
  • Figure 4 and Figure 5 all show methods used to reduce the axial space charge generated reverse electrostatic field.
  • Figure 4 shows open charged particle jet engines while Figure 5 shows enclosed structures.
  • Figure 4A shows the standard open ring configuration of Figure 3A with the applied electric field (76) shown.
  • the use of large diameter electrodes without any mesh to spread the potential across the inlet and outlet allows the potential inside the ring area to vary and as a result will lead to the electric field shown. Where the field lines are not parallel to the electrode axis, a radial component of the electric field will exist.
  • Figure 4B uses a small electrode (75) attached to each ring that can be operated at a lower potential than the ring electrodes to increase the radial electric field component causing a greater change in the radial electric field and thus a lower reverse axial electrostatic field.
  • Figure 4C uses axial electrodes to create a more uniform reverse radial electric field.
  • Figure 4D uses a plurality of electrodes whose individual potentials can be varied to achieve any desired electrostatic field configuration including a non-uniform angular as well and radial electric field component.
  • Figure 4E shows honeycomb electrodes, although they can be of any desired shape that can be used to divide up the overall input area into smaller radii regions to increase the change in the radial electric field strength.
  • Figure 5 enclosed charged particle engines are shown.
  • Figures 5A through Figure 5E correspond to the open charged particle engines of Figures 4A through Figure 4E respectively.
  • the enclosing structure can also be used as an electrode to modify the radial and/or angular electric fields.
  • the axial electrodes can also be insulated conductors or conducting channels containing oppositely charged particles whose charge density matches the charge density of the charges producing the thrust.
  • the charges in this region can simply be electrons or if it is a conductor or charged particles of opposite polarity if it is a hollow region. The point is to match the charge density at each point to partially cancel the reverse electric field of the particles producing the thrust.
  • Figure 6A shows multiple open electrodes (3), (4), and (77) with each electrode at a higher potential than the preceding electrode as shown by the multiple power supplies (78) in series.
  • Figure 6B we show an enclosed set of electrodes with the enclosure tapered to increase the charged particle and neutral reaction mass density from segment to segment.
  • Figure 7 deals with another method of increasing the charged particles between the accelerating electrodes (3) and (4).
  • the electric field at the inlet accelerating electrode (3) is reduced to zero by the space charge generated reverse electric field. If more charges somehow enter the regions between the electrodes, the electric field will actually reverse forcing charges out the front electrode ring. But we can force charges to move against this reverse electric field so that there will be a net charged particle flow into the inlet electrode.
  • One method of doing this is by the diffusion of charged particles into the inlet ring due to a concentration gradient where the charged particle density is greater outside the inlet electrode. The problem is to maintain that concentration gradient.
  • FIG 7A we show two closely spaced electrode at the inlet of the engine.
  • the additional electrode (77) provides an electric field that repels any charged particles back to the inlet electrode. While this appears to be simply a segmented engine, the functioning is different in that the spacing of the two electrodes (77) and (3) are as close as possible to maximize the charged particle concentration gradient to maximize the diffusion current. Charged particles that are accelerated out the front electrode (3) by the negative space charge generated electric field will be trapped by the opposing field set up by the applied potential between electrodes (77) and (3).
  • Figure 7B we show the use of an actual physical barrier to stop the charged particles from leaving the front of the engine.
  • the "U" shaped rings (79) form insulated regions where charged particles can be concentrated to increase the concentration gradient.
  • the physical structure of Figure 7B can be combined with the electrode structure of Figure 7A to maximize the trapping of the charged particles.
  • Electrostatic thrust is potentially much more efficient than the thermodynamic thrust generated by a conventional chemical jet or rocket. This is because the energy supplied by the electric field is initially totally in the axial direction whereas in a chemical rocket or jet engine, the thermal energy is distributed randomly in all directions. But whatever the ultimate electrostatic thrust efficiency, the energy that does not go into generating the electrostatic thrust, the energy associated with the increase in the axial component of the velocity of the neutral reaction mass, will end up it the random thermal motion of the entire reaction mass. Some of this energy can be recovered.
  • FIG 8A we show what looks line the same structure as that shown in Figure 7A , used to trap charged particles to increase the charged particle density gradient. It does that but in addition it can be used to recover some of the thermodynamic energy.
  • One way to recover some of this energy is through collisions of neutral air molecules with an axial velocity component toward the inlet electrode with the charged particles. If energy and momentum is transferred back to the charged particle either slowing the particle or reversing its direction, the charged particle will either draw less energy or return energy to the electric field.
  • the region between the accelerating electrodes (3) and (4) will recover energy while the large charge density between electrode (77) and electrode (3) will ensure that all energy associated with the neutral air mass moving toward the inlet electrode will either be recovered or will be converted into additional thermodynamic thrust.
  • thermodynamic thrust is created when the pressure in a container open on one side is greater than the ambient pressure.
  • the thermodynamic energy is the same as the thermodynamic energy caused by the burning of fuel in a chemical rocket or jet engine.
  • This thermodynamic energy appears in the form of an increase in the temperature of the reaction mass. While this temperature increase is quite small and results in a very slight increase in pressure, if the engine is operated with accelerating voltages near breakdown, the thrust associated with this increase in pressure can be an order of magnitude greater than the electrostatic thrust if the reverse electrostatic field is not reduced. To convert this increased pressure into thrust, the neutral particles moving toward the inlet electrode must be prevented from leaving the front of the engine.
  • turbojet engine we must close the inlet to the passage of neutral molecules moving out of the engine but not block them moving into the engine. It is the same problem facing a turbojet engine and all of the methods used in turbojet engine designs can be used here such as aerodynamic pressure (ram jet), inlet shutters (pulse jet), mechanical compressors (turbojets), etc. But we can also use collisions of the neutral molecules moving toward the inlet electrode with the charged particles to transfer momentum through the electric field back to accelerating electrodes. That is also what is occurring in Figure 8A when we use the high density charged particle region to recover the momentum of the forward moving neutral molecules converting it to thrust.
  • Figure 9A the separation of the accelerating electrodes of the open frame design can be varied by the telescoping electrode supports (12).
  • Figure 9B shows a telescoping enclosure using rigid sections (13), while Figure 9C shows a flexible hose type design.
  • Figures 9D through Figure 9F show an umbrella type design where the first electrode is a solid material that opens like an umbrella. In this configuration, the medium enters the region between the electrodes through the central entry region (3) and through the region below the first electrode.
  • Figure 9G shows a rectangular electrode whose area can be altered by the telescoping electrode sections.
  • Figure 9H shows an enclosed circular electrode configuration where the diameter of the enclosure can be varied by spooling and unspooling the flexible enclosing material (7).
  • Figure 10 all illustrate methods used to create vectored thrust.
  • the point of charged particle injection is not shown but is understood to be near the entry region of the medium that can change depending on the potentials applied to the individual electrode segments.
  • Figure 10A is a basic open frame configuration where the electrodes have been segmented using insulating sections (14) so that varying potentials can be applied between the segments. For example, to vector the thrust in a downward direction, the accelerating potential can be applied between the top front electrode segment and the rear bottom segment. This results in the charged particles being accelerated diagonally from top to bottom as they travel between the electrodes.
  • Figure 10B shows the segmented rectangular electrodes. Only limited thrust vectoring is possible but only a single ion injection point is needed unless bi-directional thrust is desired in which case provision must be made to supply charged particles to whichever region is acting as the medium input.
  • Figure 10D shows a cube structure where the thrust vector can be in any direction as determined by the potential applied to the individual segments.
  • Figure 10D shows a cube divided into more sections that permit finer control and greater efficiency of the thrust vector.
  • Figure 10E shows a spherical shaped structure providing even finer control. In all of these structures, means must be provided to inject charged particles at the appropriate point.
  • Figure 10F shows a flexible exhaust nozzle placed after the accelerating rings, that is used to change the vector of the exiting mass and behaves exactly the same as a directional control nozzle in a conventional vectored thrust jet engine in creating vectored thrust.
  • the electrodes are placed in the flexible enclosing material so that the electrodes also move as the nozzle is vectored causing both the neutral exhaust mass and the electrostatic force of the accelerating electrodes to be vectored.
  • Figure 10H shows a hypothetical vehicle which is enclosed in a cage of accelerating electrodes shown in Figure 11I.
  • thrust can be applied to the vehicle in any direction by varying the potentials applied to the various segments and injecting charged particles at the appropriate points.
  • Figure 11 illustrates the concept of charged particle recirculation.
  • charged particle recirculation can be used to reduce the number of charged particles that must be produced. Note that charged particle recirculation can only be used with charged particle jet engines operating in a medium because the force necessary to turn the charged particle's direction completely cancels the thrust obtained from the charged particle when it is accelerated by the electrodes. It is only because the mass of the charged particles is millions of times less than the neutral particle mass that large net thrust can be obtained without the charged particle contribution that has been neutralized.
  • Figure 11A shows a cutaway of a tube within a tube.
  • the charged particles are accelerated by the accelerating electrodes (3) and (4) and are "collected" by the exit electrode (4) where their direction is reversed either by a magnetic field or by a static or varying potential applied to the reversing electrode (15) causing the charged particles to enter the region between the two cylinders (17) and (18).
  • An opening (19) is provided in the reversing electrode to allow neutral particles to escape.
  • Varying potentials applied to the reverse acceleration electrodes (16) accelerate the charged particles giving them sufficient energy to "make it back up the potential hill". It is important to note that if the charged particles are not neutralized by the exit electrode the forward accelerating electrodes do not supply any net energy to the charged particles. This occurs because any energy that the charged particle obtains from the accelerating rings traveling from the entry ring (3) to the exit ring (4) is returned when the charged particle returns to the entry electrode.
  • a reversing electrode (15) or a magnetic field again alters the direction of the charged particles injecting them again into the entry region between the two accelerating electrodes. It is important to note that any neutral particles that are accelerated along with the charged particles in the return region (17) will transfer their energy in the form of forward thrust when they can't make the turn at the end of the return region (17) and collide with the end of the region.
  • Figure 11B and Figure 11C show three-dimensional detail views of the ends of the charged particle return region.
  • Figures 11D through Figure 11F show a recirculation structure axially located in the center of the acceleration region. It is also possible that both an outer and inner recirculation path are used as forward thrust efficiency will be increased by the more uniform electrostatic field of inner and outer electrodes and the more uniform injection of the recirculated charges.
  • Figure 12 shows detailed cutaway cross sectional views of several possible electrode structures.
  • Figures 12A through Figures 12D have rectangular cross-sections that provide greater axial strength at the expense of streamlining.
  • Figures 12E through Figure 12H have round cross sections that present less drag than the rectangular cross sections with less axial strength.
  • the square cross sections of Figures 12I through Figure 12K provide both radial and axial strength at the expense of streamlining.
  • Figures 12L through Figure 12O are cross sections of streamlined electrodes that result in the axial strength of the rectangular cross section with low drag.
  • Each of the cross sectional shape groups contains hollow electrodes with an opening pointing in various directions. They represent electrodes where the charged particle generator or injector is contained in the electrode and the openings are used to inject the charged particles either into the medium before it enters the region between the electrodes, across the electrodes to distribute the charged particles uniformly across the input area, and toward the exit region of the engine which can be used for exit electrodes for engines that produce vectored bi-directional thrust.
  • Figure 12O shows a streamlined cross sectional area where the leading edge is a transparent lens used with some photon ionization methods.
  • Figure 13 shows various enhancements to electrode structures to create a more uniform electric field between the two accelerating electrodes.
  • a wire mesh or grille is used to create a flat electrical potential plane that results in a more uniform electric field between the electrodes.
  • Figure 13B uses concentric rings that results in a stronger more rigid unit at the expense of field uniformity.
  • the thrust force is applied to the electrode and the mesh or rings connected to it so these structures must be made strong enough to handle this thrust force.
  • Figure 13C presents the concentric rings as a cone shape resulting in greater strength than the other two structures. While the electrode structures are shown as rings it is obvious that these methods used to enhance electrode properties can be applied to electrodes using other geometries.
  • Figure 14 shows possible electrode structures modified to facilitate charged particle generation and injection into the ring area.
  • the inside surface of the electrode forms a parabolic mirror so that photons used in photon ionization of the medium are bounced continuously across the area enclosed by the electrode to minimize the energy lost to photons that do not ionize an atom or molecule of the medium.
  • Figure 14B shows the photons being reflected around the interior of the region enclosed by the electrode. In actual practice, the photon distribution could be uniform around the electrode but may be concentrated into focused beams to enhance the ionization rate.
  • the cone of concentric rings with internal reflectors, stronger under compressive loads, is used to create a volume where the photons will be contained within the region enclosed by the electrode.
  • Figures 15 and 16 show methods of obtaining charged particles for use in the charged particle jet engine.
  • charged particles we divide charged particles into two classes, traditional positive and negative ions and larger particles that have been given a positive or negative electric charge.
  • Positive ions can be created by the absorption of photons by the bound electrons of the atom or molecule. If they absorb sufficient energy, the electron will be completely removed from the atom or molecule leaving the atom or molecule with a net positive charge.
  • Both positive and negative ions can be created by bombarding an atom or molecule with some particle, usually an electron, that is either captured by the atom or molecule forming a negative ion or by transferring sufficient energy (24) to an electron bound to the atom or molecule such that the bound electron is completely removed from the atom or molecule leaving the atom or molecule with a net positive charge.
  • Non-ionic charged particles are larger particles that have acquired either a positive or negative charge. This includes materials that are manufactured with a permanent positive or negative charge.
  • Figure 15 shows several methods of using electromagnetic waves to generate ions directly in the vicinity of the medium entry region of the engine or in separate structures surrounding the outside periphery of the entry accelerating electrode. While the charged particle generator of Figure2B shows the charged particle generator as a separate structure, the methods shown in Figure 15A through Figure 15K incorporate the charged particle generator in the electrodes themselves.
  • Electromagnetic waves can be an efficient way of generating ions. Photons of electromagnetic radiation are readily absorbed by electrons surrounding atoms and molecules. If the energy of the photon is greater than the ionization energy of an atom or molecule, a single photon will ionize each ion or molecule. Ignoring the possibility of capturing two photons by a single atom or molecule, single photon ionization will be nearly 100% efficient. Unfortunately for oxygen and nitrogen, the ionization energy is in the 15 electron volt range corresponding to very short wavelength ultraviolet radiation. High output short wavelength efficient ultraviolet light sources are currently in development but are not available yet. When they are available, they will be the preferred choice for electromagnetic wave ion generation.
  • Multiple photon ionization is less efficient because a single atom that has absorbed one or more photons must absorb the remaining photons before the energy of the preceding photons is radiated away. Additionally, if an atom has not absorbed sufficient photons to become fully ionized before it moves out of the region where these photons exist, the energy of the absorbed photons will again be lost.
  • the way to maximize ion creation using the minimum amount of energy is to use as few photons as possible to ionize each atom or molecule. Visible light will require five to eight photons to fully ionize an oxygen or nitrogen atom. This leads to some of the approaches shown in Figure 15 .
  • the photons (20) are aimed ahead of the engine so that atoms and molecules of the medium remain in the ionization region filled with photons for a longer period of time.
  • the photons (20) from multiple rings (21) are aimed forward.
  • Figure 15E and Figure 15F the photons (20) are reflected across the area enclosed by the electrode (21) but the length of the electrode is increased to create a larger ionization volume.
  • Figures 15G through 15J illustrate narrow electrodes (21) with a short ionization region that would be advantageous when single photon ionization is used.
  • the ion and its emitted electron must be separated to prevent them from recombining. This is easily accomplished by using an electric field to separate the ion and electron.
  • fringing electric fields will reach ahead of the electrode and can be used for this purpose as shown in Figure 15K where the ion is (23), the electron is (22), the electric field is (24) and the accelerating electrodes are (3) and (4).
  • the problem with multiple photon ionization is that the photon beam intensity must be high for the probability of multiple photon capture to be high yet only one in several million atoms needs to be ionized.
  • One way to deal with these conflicting requirements is to focus the photons into narrow beams so that the photon density is high in the beams while only a very few atoms and molecules are exposed to the photon beam. This can be done with all the methods shown in Figures 15A through Figure 15J by focusing the photons into these high intensity beams.
  • an electromagnetic wave ionizer is shown that is separate from the accelerating electrodes.
  • a very small tube (25) is used to contain both the photons and molecules.
  • the entire interior surface is made of a highly reflective insulating material and the photons are admitted from the photon source (21) by either an aperture or a partially reflective mirror (26). Once in the cavity, the photons remain trapped as long as possible.
  • Neutral atoms and molecules from the medium are introduced through small openings in the chamber (28) and (29). Opening (28) is only needed if insufficient neutral atoms and molecules are able to swim against the tide of ions leaving opening (29).
  • Electrodes (27), (30) and (31) separate the ion from the electron by a small electric field between electrodes (30) and (31) and electrode (27). Electrode (27) collects the electrons while the ions are directed out a small opening (29). Electrodes (30) and (31) form electrostatic deflection plates to sweep the ions through a wide volume to reduce the space charge density as quickly as possible and spread the ions uniformly throughout the selected region.
  • Figure 15N shows a cutaway of a ring electrode showing the ion generator of Figures 15L and 15M attached to the electrode and the slots through the electrode that are used to inject the ions into the area surrounded by the electrode.
  • Figure 16 shows the use of methods other than electromagnetic ion creation to supply the required ions.
  • Figures 16A through Figure 16R all generate charged particles by ionizing the gaseous or fluid medium. While ionization using electromagnetic radiation can only create positive ions by removing electrons, the methods shown in Figure 16 can be used for both positive and negative ions.
  • Figures 16A through Figure 16D show the basic "corona discharge" ionization structure where a sharp pointed electrode (32) is placed near a second large area electrode (33).
  • the pointed electrode (32) is hollow and has a channel (45) that is the only way the atoms and molecules of the medium can enter into the region between the two electrodes.
  • Figure 16B shows the structure of Figure 16A with the corona discharge voltage applied by a high voltage power supply (8) to the two ionization electrodes (32) and (33).
  • the polarity of the applied voltage, the sharp pointed electrode positive and the large flat electrode negative, is such that positive ions will be created.
  • Figure 16C and Figure 16D show the structure of Figure 16A with the polarity of the of the power supply reversed to generate negative ions.
  • the positive ion (23) has already been created by the removal of an electron (22) from the atom or molecule.
  • the high electric field between the two electrodes (32) and (33) separates the ion (23) from its electron (22) by accelerating the ion and electron away from each other as shown by the ion trajectory (47) and the electron trajectory (46).
  • a conventional corona discharge ionizer it would not matter where between the two electrodes (32) and (33) the ion (23) was created since the total energy obtained by the ion (23) and electron (22) together would be the same regardless of the creation point.
  • the ion (23) will have a greater share of the energy as it is accelerated toward the flat electrode (33) while if the ion (23) is created nearer the flat plate electrode (33), the electron (22) will acquire more energy than will the ion (23). If the created ions (23) are to be of any use, they must not be allowed to contact the flat plate electrode (33) or they will both be neutralized and the kinetic energy of the ion (23) obtained from the field between the two electrodes (32) and (33) will be transferred to the plate electrode (33) in the form of heat when the ion (23) impacts the plate electrode (33).
  • the electron (22) that was removed from the neutral atom or molecule could still acquire a great deal of energy if the ion (23) is created near the plate electrode (33).
  • FIG 16E we show one method that can be used to prevent collisions of the ions with the plate electrode.
  • An enhancement to this method is to place one pole of a magnet (36) on one side of the plate (33) and the other pole (37) on the opposite side of the plate (33).
  • deceleration electrode (35) on the side of the plate electrode (33) opposite the pointed electrode (32) and separated from the plate electrode (33) by an insulator (34).
  • This electrode (35) is used to slow the ions (23) once they have passed through the hole in the plate electrode (33).
  • the potential applied to the deceleration electrode (33) referenced to the pointed electrode (32) must be sufficient to prevent the ion from stopping and falling back to the plate electrode.
  • the potential between the pointed electrode (32) and the plate electrode (33) is 10,000 volts and the ion (23) is created right at the pointed electrode (32) so that it has acquired 10,000 electron volts of energy by the time it reaches the plate electrode (33), applying zero volts between the pointed electrode (32) and the deceleration electrode (35) will cause the ion (23) to have zero energy when it reaches the deceleration electrode (35).
  • the potential applied between the pointed electrode (32) and the deceleration electrode (35) will set the final energy of the ions (23) leaving the ionizer and not the potential applied between the pointed electrode (32) and the plate electrode (33) as would be the case if we used the accelerating electrodes (3) and (4) of the ion jet to generate the ions (23).
  • the deceleration electrode (35) voltage must be set to prevent the majority of ions (23) from falling back onto the plate electrode (33), any energy lost by collisions of the ions (23) with other particles must be minimized to limit the spread of energies of ions (23) leaving the ionizer. For this reason, the number of neutral atoms and molecules must be limited in the region between the pointed electrode (32) and the deceleration electrode (35). By having the medium enter through the pointed electrode (45) in a controlled fashion, the number of neutral atoms and molecules between the pointed electrode (32) and the plate electrode (33) are minimized.
  • the ions (23) By setting the potential of the deceleration electrode (35) at a value that leaves the ions (23) with a small amount of energy at the deceleration plate (35), the ions (23) will act as an ion pump, removing neutral atoms and molecules from the region between the pointed electrode (32) and the deceleration electrode (35).
  • Figure 16G shows a cross-sectional view of the plate electrode (33), deceleration electrode (35), the magnetic pole pieces (36) and (37), the insulator (34) between the plate electrode (33) and deceleration electrode (35), and the magnetic field (39) produced by the magnetic pole pieces (36) and (37).
  • Figure 16H shows a cross-sectional view of the plate electrode (33), deceleration electrode (35), the magnetic pole pieces (36) and (37), the insulator (34) between the plate electrode (33) and deceleration electrode (35), and the accelerating electrostatic field (40) produced by the potential applied between the pointed electrode (32) and the plate electrode (33) and the decelerating electric field (41) produced by the potential applied between the plate electrode (33) and the deceleration electrode (35).
  • Figure 16I shows a more detailed cross section showing a single acceleration field line (40) and single deceleration field line (41).
  • Figure 16J shows the superposition of a single acceleration field line (40), single deceleration field line (41), and a single magnetic field line (39).
  • Figure 16K shows a cross section of the completely enclosed ionizer.
  • the entire set of electrodes is sealed from the medium by the enclosure (42) and (43).
  • the medium enters through the hollow pointed electrode (32) through the tube (45) and the ions (23) leave through the exit opening (44).
  • Figure 16L shows the same structure as the ionizer of Figure 16K but the electrodes are now two-dimensional for increased ion production. Instead of a pointed electrode (32) it is now a hollow blade electrode (32) and the other electrode shapes are now rectangular with a slot through the plate electrode (33), insulator (34) and deceleration electrode (35). The exit opening (44) has also been changed to a slot. While both one-dimensional "point” electrodes and two dimensional "line” electrodes have been shown it is obvious that the two-dimensional straight line can be made of any arbitrary two-dimensional shape.
  • Figure 16M shows an alternative structure for creating ions (23) using a large electrostatic field.
  • the electrostatic field is used to create the ions (23) and a magnetic field (39) is used to keep the ions (23) from hitting plate electrode (33) while at the same time they are being decelerated by the deceleration electrode (35).
  • a magnetic field (39) perpendicular to the accelerating electric field is used to make the ions (23) follow a curved trajectory (47) away from the plate electrode (33).
  • the deceleration electrode is now funnel shaped to both decelerate the ions and focus them so that they will pass through the exit opening (44).
  • Figure 16N shows a top view of the ionizer to better show the ion (23) trajectory (47) and electron (22) trajectory (46).
  • Figure 16O shows the ionizer inside an enclosure to control the entry of the medium into the ionizer.
  • Figure 16P shows the two-dimensional blade electrode configuration equivalent to the Figure 16L .
  • Figure 16Q shows the decelerating electric field (41) between the plate electrode (33) and the deceleration electrode (35).
  • the electric field (41) that is used to decelerate the ions also focuses the ions into the funnel since the electric field is in a direction to force the ions away from the deceleration electrode (35).
  • Figure 16R shows both the accelerating electric field (40) and decelerating electric field (41) where the decelerating electrode (35) is perpendicular to accelerating electric field (40).
  • the angle that the decelerating electrode (35) makes with the accelerating electric field (40) can be varied to change the angle between the input (45) and output (44) regions as the need arises.
  • Figure 16S shows a laser beam (48) focused at the tip of the pointed electrode to enhance the creation of positive ions (23) near the pointed electrode (32) to both lower the potential that must be applied between the pointed electrode (32) and the plate electrode (33).
  • the pointed electrode has been modified with the addition of an electron source (50).
  • the electron source can be used as the source of electrons to be captured by the neutral atoms and/or molecules.
  • the electrons from the electron source can be injected into the pointed electrode with sufficient energy to knock electrons from the neutral atoms and/or molecules creating positive ions. These electrons must have sufficient energy to have enough energy remaining after it has transferred energy to the electron removed from the atom or molecule when the ion is created to ensure that it will not be captured by the ion thus just swapping electrons but not creating ions.
  • One of the problems with most electron sources is that they are either relatively inefficient as are thermally emitted electrons or they are created with relatively high energies when cold cathodes or field emission is used.
  • a decelerating field can also be used to recover energy from electrons that are created with high energy as a byproduct of creation process.
  • three electrodes, the electron source electrode (50), the electron deceleration electrode (53) and the pointed electrode (32) are used to control the behavior of the electrons supplied by the electron source (50).
  • the potential (49) applied between the electron source (50) and the deceleration electrode (53) determines the energy of the electrons at the medium entrance point (45) after being accelerated by the electric field (51).
  • the potential applied between the electron deceleration electrode (53) and the pointed electrode (32) determines the electron energy as it is being accelerated by the electric field (52) in the region where the electrons collide with the medium to produce the ions.
  • the electrons can be slowed to the point where electron capture is maximized.
  • the energy can be set to the minimum value necessary to strip electrons from the medium without the colliding electrons being captured.
  • the laser enhanced ionizer of Figure 16S can be used with the electron generation ionizer of Figure 16T to enhance the production of positive ions with minimum energy spread and minimum ion energy.
  • Figure 16U shows the pointed ionizer electrode (32) being fed ionizing material from a tank (57) through a pipe (56) to a collar (55) containing a passage (54) around the pointed ionizer electrode. While the material (59) is shown as either a liquid or solid for clarity, it could also be a gas. The tank is filled through the filler (58). Not shown is a return tube to the tank where neutralized ions from the ion recirculator can be returned to the tank when no longer needed.
  • both deflection plates are biased with respect to the interior of the tank to produce an electric field that keeps the charged particles in the tank, varying that field can be used to control the number of charged particles removed from the tank.
  • varying that field can be used to control the number of charged particles removed from the tank.
  • a molecule (1) is traveling toward a wall (7). When it collides with the wall in Figure 17B , it stops and transfers its energy to the wall. In Figure 17C , the wall rebounds and returns some of the energy to the molecule (1) but as shown by the length of the arrow in Figure 17D , some energy is lost to the wall, reducing the speed of the molecule (1) and heating up the wall (7).
  • a thin layer of charged particles (23) placed between the molecule and the wall (7) made of an insulating material can be used to shield the wall (7) from the molecules (1).
  • the charged particles (23) repel each other and when one is hit by a neutral molecule (1) in Figure 17F , it moves toward the other charged particles (23).
  • the molecule (1) transfers its energy to the charged particles (23) that by their motion transfer the energy of the molecule (1) to the electric field between the charged particles (23).
  • the charged particles (23) will rebound returning the energy to any molecules (1) it hits as shown in Figure 12G .
  • the length of the arrow in Figure 17H more of the energy is returned to the molecules (1) due to the collisions with the charged particles (23) being more elastic. With less energy removed from the molecules per collision, drag is reduced, as is the heating of the wall.
  • Figure 17M shows an enlarged cutaway view of the region (62) of Figure 17N .
  • the ion generator is the ion generator of Figure 11L wrapped around the tube (7) of Figure 17N .
  • the ion generator admits the medium through the inlet (45) and the hollow pointed electrode (32).
  • the ion is created by the high voltage between the pointed electrode (32) and plate electrode (33) separated by insulated supports (63).
  • the created ions pass through a hole in the plate electrode and are then slowed by the deceleration electrode (35).
  • the ions are then split and leave the ion generator through the two exit ports (44). These ions spread out over both surfaces of the tube (7).
  • Embedded in the tube wall is an electrode (4) that attracts the ions to both sides of the tube. This charged particle shield can easily be applied to the charged particle jet engine.
  • Figure 18A is a view of a complete self-contained unidirectional charged particle engine, one of many possible designs.
  • ions are generated by a self-contained ion generator near the front ring with the medium intakes for the ion generator (45) at the front of the engine.
  • Figure 18B is a cutaway of the device shown in Figure 18A .
  • the ionizer surrounds the input electrode (3) and takes in air through the openings (45) and injects the created ions through the opening (44) just after the input electrode (3) inside the enclosed tube.
  • Surrounding the jet tube (7) is a fuel cell (61) and the fuel for the fuel cell (60).
  • the power supply (8) is located at the rear of the engine. This self-contained unit forms a complete charged particle jet engine.
  • the engine shown in Figures 18C through Figure 18E is a bi-directional charged particle jet engine that integrates the corona discharge ion generator of Figure 11L with the electrodes (32), (33) and (35) placed radially behind each of the rings (62).
  • the ion generator is shown in detail in Figure 18C .
  • This unit gets its power from an external source although it could also use the same self-contained power source shown in Figure 18A and Figure 18B .
  • Figure 19 illustrates many land based uses for the charged particle jet engine.
  • Figures 19A and Figure 19B show a load (66) suspended below four of the self-contained modular charged particle jet engines (64) of Figure 19 by cables (65).
  • charged particle engines can take the place of forklifts, construction cranes, logging transporters, and other applications where a load must be lifted or moved. With the use of vectored thrust, these lifters cannot only lift the load but they can move the load in any direction.
  • the lifter of Figure 19A clusters the engines so that if one fails, the others can compensate for the lost engine.
  • the lifter in Figure 19B has the engines moved to the corners of the lifting platform (67) so that the accelerated air from the engines (64) do not impact on the platform (67) and the platform (67) can automatically be leveled by controlling the thrust of the four engines.
  • the Omnijet of Figure 19C is a vehicle with multiple electrodes to provide vectored thrust in any direction and when operated on land near the ground can operate as a ground effects vehicle to lessen thrust requirements.
  • Figure 19D is a simple fan using the charged particle jet. Its simplicity, efficiency light weight and lack of moving parts make for a very cost effective fan.
  • Figure 19E is a simple compressor using the charged particle jet.
  • Figure 19F shows the use of a flat charged particle jet to construct a floating skateboard. Again, vectored thrust and/or shifting body weight can be used to provide motion in any direction.
  • Figure 19G is a dedicated version of a ground effect vehicle.
  • the two charged particle jets facing down provide the ground effect air while the charged particle jet in the back provides forward and backward thrust.
  • Directional control can again be obtained through vectored thrust.
  • Figure 19H is a conventional automobile retrofitted with a charged particle jet engine.
  • the engine is placed under the floor pan with a large intake and exhaust.
  • Figure 19I shows an automobile that has been designed specifically for a charged particle engine.
  • the automobile is designed to maximize the mass of air moved to maximize efficiency.
  • Vectored thrust could be incorporated to improve road handling and the smoothness of the ride.
  • Figure 19J and Figure 19K show the use of a charged particle jet engine as a ground effect machine constrained in its motion by a track (69).
  • the two charged particle electrodes (3) and (4) provide forward and backward thrust.
  • Figure 19J shows a sectioned cutaway that shows a second set of electrodes (3) and (4) to force air under the vehicle to provide a ground effect cushion.
  • the tracks (69) could be made out of any cheap material that can be extruded along the desired path.
  • Figure 19L shows the vehicle (68) of Figure 19K operating in an enclosed tube (70). This would increase efficiency and could be used as both a subway below ground or as a suspended monorail above the ground.
  • Figure 19M shows the vehicle (68) of Figure 19K operated vertically as an elevator constrained in its motion by a shaft (71) through which it travels.
  • Figure 20 shows many water-based applications of the charged particle jet engine. While the ion source for the engine may differ from air based engines, the principles are the same. Because we are now dealing with a much denser liquid, smaller devices can be used for a given thrust and efficiency.
  • Figure 20A shows the skateboard of Figure 19F which can certainly be used over water. It can either use air as a skimmer over water or it could run on the surface like a self-propelled surfboard. Again, vectored thrust and/or shifting body weight can be used for steering and to keep the input of the board just under the surface of the water.
  • Figure 20B is a simple water pump that is again, simple light weight, efficient, and with no moving parts.
  • Figure 20C is the ground effects machine of Figure 20G operating over water. Like current ground effect machines, the charged particle jet ground effect vehicle would operate equally well over land and water since it would use air for both lift and propulsion.
  • Figure 20D and Figure 20E show conventional boats powered by charged particle jet engines (64).
  • Figure 20D shows an inboard where the jets run through the hull to minimize the draft of the boat.
  • Figure 20E shows an outboard (64) at the stern of the boat. Both vectored thrust and/or rotation of the engine can be used for steering.
  • Figure 20F shows a float or dock that is kept afloat by charged particle jets (64). Because of the increased density of water compared to air, greater thrust can be obtained using much less energy than would be need if air were used.
  • One advantage of the use of charged particle jets (64) to float a platform (67) is that they can be used to keep the platform level as both the load shifts on the platform (67) and as it is rocked by waves.
  • the charged particle jets do not have to supply all the buoyancy and can in fact just be stabilizers on a conventional buoyant floating platform.
  • Figure 20G shows the Omnijet which can be used both on the water and below it if so designed. While the ion generators may have to be modified for dual medium use, the principles are again the same.
  • Figure 20H shows a charged particle jet (64) attached to the boots of a person which can propel the person above, across or below the water. Active control of the magnitude and direction of thrust can provide dynamic stability without other complex mechanisms.
  • Figure 20I shows a torpedo with the streamlined payload (72) ahead of the charged particle jet engine (64). Due to the simplicity, light weight, and efficiency, the speed, range and payload should be far greater than current devices.
  • Figure 20J shows a charged particle jet (64) used as a personal propulsion device for a diver.
  • Figure 20K shows a submarine built around charged particle jets for propulsion.
  • the multiple electrodes (3,4) are used to provide vectored thrust in all directions.
  • Figure 20L and Figure 20M are the lifters of Figure 19A and Figure 19B that can be used to raise various objects from the sea floor.
  • Figure 21 shows various uses of the charged particle jet engine in the atmospheric and in space applications.
  • Figure 21A shows a vehicle for use at very high altitudes where the air density is very low.
  • the large area jet rings help maintain relatively high efficiency at useful thrust levels.
  • 100-foot diameter rings can produce 5,000 pounds of thrust using less than 100 kilowatts.
  • these same rings can produce the same 5,000 pounds of thrust using only a megawatt of power.
  • Two hundred foot rings reduce the energy needed to produce 5,000 pounds of thrust to 360 kilowatts.
  • the medium through which the vehicle passes still contains a small particle density.
  • the mechanism shown in Figure 21B can be used to concentrate 35 these particles to increase thrust efficiency. This approach can also be used in the atmosphere to increase the density of the air entering the jet. While in theory, the size of the rings can simply be increased to compensate for the thin air density, eventually weight and strength become limiting factors in the size of the rings. In addition, using the same electric field strength for different medium densities is not very efficient.
  • the large pair of rings (3A) and (4A) form a charged particle jet engine. These rings are lightweight flexible structures that can be contained inside the actual vehicle and deployed when needed for added efficiency. These large rings when deployed are attached to the vehicle using long flexible wires (73) that also pass power to these rings.
  • FIG 21C we show a conventional SR71 type aircraft retrofitted with charged particle jet engines (64). Unlike conventional jet engines, the exhaust velocity of the charged particle jet engines can be much greater than the exhaust velocity of chemical jet or rocket engines.
  • Figure 21E shows a conventional blimp retrofitted with charged particle engines (64). These engines should produce much greater thrust for a given engine weight.
  • Figure 21F is a new blimp design that can produce thrust in any direction. This can help stabilize the blimp in gusty weather.
  • Figure 21G shows charged particle jets retrofitted to a large capacity cargo plane. While the large energy requirements may make heavy lifter development slower than lighter weight applications, in time, these high power sources will be developed.
  • Figure 21H is a new design for a general aviation aircraft based on charged particle jet engines. Because of the light weight of the charged particle jet engine, small lightweight personal aircraft should now be possible at a reasonable cost.
  • Figure 21I is the same personal flying suit shown in Figure 20H .
  • Charged particle jet engines attached to the boots will give the person the sensation of simply standing on the ground as the thrust force will simply be through the feet.
  • Small auxiliary charged particle jets attached to the hands give added control and stability. Active control of the magnitude and direction of thrust can provide dynamic stability without other complex mechanisms.
  • Figure 21J is a large area charged particle jet engine that can be used as a solar powered surveillance platform that could stay airborne for weeks at a time.
  • Figure 21K is a variation on the flying suit where the ion jets are attached to the person's sides. This configuration is more stable but is probably not as comfortable.
  • Figure 21L is once again the Omnijet that can be used on land, sea, and air.
  • the final Figure 21M is a guided missile. Like the torpedo, it is simply a warhead (72) with control electronics attached to a charged particle jet (64).
  • the charged particle jet missile should be unmatched for both speed and range due to the light weight of the charged particle jet engine and its far greater efficiency over chemical rockets and jets.
  • the present invention provides some preferred embodiments described in the following list:

Claims (15)

  1. Dispositif de moteur de projection de particules chargées comprenant :
    une pluralité d'électrodes connectées à au moins une source de puissance électrique ;
    au moins l'une desdites électrodes (3, 4), lorsqu'elle est immergée dans un milieu gazeux, étant configurée pour permettre au milieu de passer à travers ou autour de celui-ci ;
    dans lequel la taille, la forme, et la position des électrodes (3, 4) dans le milieu créent différentes régions du milieu utilisé par le dispositif ;
    des particules chargées de faible énergie introduites au niveau de n'importe quel point dans ledit milieu ou
    séparées des autres particules chargées qui sont déjà dans le milieu de sorte que la majeure partie des particules chargées dans une région sont d'une même polarité ;
    dans lequel ces particules chargées sont accélérées par un ou plusieurs champs électriques produits par des différences de potentiel entre les électrodes ;
    dans lequel les particules chargées accélérées parcourent une distance dans le milieu de sorte que le nombre de collisions desdites particules chargées accélérées avec des atomes et/ou des molécules du milieu résultent en le transfert d'énergie et d'une quantité de mouvement des particules chargées aux atomes ou molécules neutres ;
    dans lequel la masse totale des atomes et/ou des molécules neutres qui entrent en collision avec les particules chargées dépasse la masse totale des particules chargées ;
    dans lequel l'énergie et la quantité de mouvement des atomes et/ou des molécules neutres qui sont entrés en collision avec les particules chargées accélérées dépassent l'énergie et la quantité de mouvement des particules chargées accélérées après avoir quitté la région du dispositif où les particules chargées ont été accélérées ;
    dans lequel toutes les électrodes où les particules chargées sont neutralisées après avoir atteint et/ou être passées à travers ou autour desdites électrodes sont définies en tant qu'électrodes de sortie ; et
    dans lequel au moins deux des électrodes établissent un champ électrique, et
    caractérisé en ce que
    des moyens sont prévus pour réduire le champ électrique généré par les charges d'espace axial produit lorsque les charges sont entre les électrodes.
  2. Dispositif de moteur de projection de particules chargées selon la revendication 1, dans lequel il est prévu des électrodes supplémentaires situées entre les électrodes d'accélération (3, 4) pour créer un champ électrique radial, et/ou angulaire,
    dans lequel ces électrodes supplémentaires sont les moyens pour réduire le champ électrique généré par les charges d'espace axial.
  3. Dispositif de moteur de projection de particules chargées selon la revendication 1,
    dans lequel le champ électrique généré par les charges d'espace axial est réduit par un champ électrique non uniforme perpendiculaire au champ électrique généré par les charges d'espace axial.
  4. Dispositif de moteur de projection de particules chargées selon la revendication 1,
    dans lequel le champ électrique généré par les charges d'espace axial est réduit par une densité de charges non uniforme.
  5. Dispositif de moteur de projection de particules chargées selon la revendication 1,
    dans lequel le champ électrique généré par les charges d'espace axial est réduit par des canaux isolés de particules chargées axiaux.
  6. Dispositif de moteur de projection de particules chargées selon la revendication 1,
    dans lequel le champ électrique généré par les charges d'espace axial est réduit par au moins une région de production de poussée axiale dans laquelle les particules chargées ont une polarité où les champs électriques générés par les charges d'espace d'au moins l'une des régions peuvent être amenés à annuler partiellement ou complètement les champs électriques générés par les charges d'espace d'au moins l'une des régions.
  7. Dispositif de moteur de projection de particules chargées selon la revendication 6, dans lequel le champ électrique généré par les charges d'espace axial est réduit par au moins une région de production de poussée axiale dans laquelle les particules chargées ont une polarité où les champs électriques générés par les charges d'espace d'au moins l'une des régions peuvent être amenés à annuler partiellement ou complètement les champs électriques générés par les charges d'espace d'au moins l'une des régions et où les régions sont coaxiales.
  8. Dispositif de moteur de projection de particules chargées selon la revendication 1, dans lequel le dispositif comprend des régions de production de poussée et dans lequel les régions de production de poussée sont segmentées pour créer une poussée supplémentaire.
  9. Dispositif de moteur de projection de particules chargées selon la revendication 8, dans lequel des électrodes supplémentaires sont utilisées pour segmenter les régions de production de poussée pour créer une poussée supplémentaire et dans lequel chaque électrode suivante est mise en oeuvre à un potentiel plus élevé que celui de l'électrode avant celle-ci.
  10. Dispositif de moteur de projection de particules chargées selon la revendication 1, dans lequel les particules chargées sont neutralisées lorsqu'elles ne sont plus nécessaires.
  11. Dispositif de moteur de projection de particules chargées selon la revendication 1, comprenant en outre un recirculateur d'ions pour faire recirculer les particules chargées d'une région où les particules chargées ne sont plus utiles de retour vers une région où elles peuvent être utilisées de nouveau.
  12. Dispositif de moteur de projection de particules chargées selon la revendication 1, dans lequel la trajectoire des particules chargées est modifiée pour changer la direction de l'accélération des particules, produisant ainsi une poussée vectorisée.
  13. Dispositif de moteur de projection de particules chargées selon la revendication 1, dans lequel au moins deux des électrodes comprennent un générateur d'ions et dans lequel des particules chargées sont introduites dans une ou plusieurs régions par ionisation directe des atomes et/ou des molécules provenant du milieu dans la région.
  14. Procédé pour générer une poussée dans un moteur de projection de particules chargées fonctionnant dans un milieu gazeux, comprenant :
    la fourniture d'au moins deux premières électrodes (32, 33) pour ioniser les particules dans le milieu ;
    la fourniture d'un premier potentiel électrostatique entre deux des premières électrodes de génération d'ions pour créer des particules chargées dans le milieu ;
    la fourniture d'au moins une ou plusieurs électrodes secondaires pour accélérer les ions générés par les premières électrodes ;
    la fourniture d'un deuxième potentiel électrostatique différent entre deux des électrodes d'accélération ; et
    la commande de la tension d'accélération de manière indépendante de la tension utilisée pour la génération d'ions,
    dans lequel les particules chargées produisant une poussée génèrent un champ électrique inverse qui s'oppose au champ électrique d'accélération généré par les deuxièmes électrodes, le procédé étant caractérisé en ce qu'il comprend en outre
    la modification du champ électrique radial pour améliorer le champ électrique radial et pour, de ce fait, réduire l'intensité du champ axial inverse.
  15. Procédé selon la revendication 14 comprenant en outre :
    l'intégration de régions de transport de courant entre les électrodes d'accélération, les régions de transport de courant générant des particules chargées de manière opposée dont le champ électrique généré par les charges d'espace s'oppose au champ électrique inverse des particules de génération de poussée, ou le neutralise.
EP05858401.2A 2004-09-03 2005-09-02 Moteur de poussee a particules chargees Active EP1797319B1 (fr)

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US60740504P 2004-09-03 2004-09-03
US11/219,047 US7584601B2 (en) 2004-09-03 2005-09-01 Charged particle thrust engine
PCT/US2005/031568 WO2007008234A2 (fr) 2004-09-03 2005-09-02 Moteur de poussee a particules chargees

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FRANCIS X CANNING ET AL: "Asymmetrical Capacitors for Propulsion", TECHNICAL REPORT NASA/CR-2004-213312, 12 October 2004 (2004-10-12), XP055312027, Retrieved from the Internet <URL:https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20040171929.pdf> [retrieved on 20161019] *
K. MASUYAMA ET AL: "On the performance of electrohydrodynamic propulsion", ROYAL SOCIETY OF LONDON. PROCEEDINGS. MATHEMATICAL, PHYSICAL AND ENGINEERING SCIENCES, vol. 110, no. 754, 3 April 2013 (2013-04-03), GB, pages 341 - 20120623, XP055312017, ISSN: 1364-5021, DOI: 10.1098/rspa.1926.0019 *

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EP1797319A2 (fr) 2007-06-20
EP1797319A4 (fr) 2014-07-09
WO2007008234A3 (fr) 2008-11-20
US20090288385A1 (en) 2009-11-26
WO2007008234A2 (fr) 2007-01-18
US7584601B2 (en) 2009-09-08
ES2709423T3 (es) 2019-04-16
US8112982B2 (en) 2012-02-14
US20060283171A1 (en) 2006-12-21
WO2007008234A4 (fr) 2008-12-31

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